The Boeing Company

Ian E Schroeder

Jiangtian Cheng

Clifford D Borowicz

Eric Sean Kamila

Kanna M Pham

Samuel Eric Cregger

Scott M Spencer

Chilip Chan

Kristopher William Talcott

Gary D Swanson

Josephine LaCoe

Roozbeh Chavoshian

Joseph Lee Sweetin, Iii

Jason H Inouye

Kurtis Shuldberg Willden

Aaron William Bartel

Randall Dow Wilkerson

Steven Paul Walker

Richard Bruce Tanner

Patrick Bickford Stickler

Dan Dresskell Day

Forouzan Behzadpour

Lisa Christina Carlson

Khanh Mai Pham

David Eric Gideon

Gagandeep Saini

Samuel L Block

Richard R Rosman

Gary D Oakes

Melinda Dae Miller

Jesse Randal Wiseman

Brett D Whitmer

Steven Kuan-chi Wu

Tho Ngoc Dang

Tyler W Downey

Greg M Reyneke

William H Graham

Gregory A Cass

Mark Edmond Shadell

Kristin L Hall

Kin M Ng

Jean R Paillant

Megan C Kinney

Thanh Quach

Melissa A Uhlman

John A Davies

David E Gideon

Composite assemblies are described that include composite spars that are co-cured with one or more sacrificial members on their flanges, forming an integrated sacrificial surface for the composite spars. In one embodiment, the composite assembly includes a composite spar having a web and flanges that project from sides of the web. The composite assembly further includes a sacrificial member of composite materials co-cured with the composite spar on an outer surface of at least one of the flanges. In addition, the sacrificial member has an outer surface that has been machined into conformance with an inner surface of at least one skin panel for an aircraft structure to form a contact surface with the at least one skin panel.

Composite spars with integrated sacrificial surfaces

Provided are stiffened stringer panels with integrated shim structures. An example composite panel comprises a skin member having an inner surface, and a stringer positioned on the inner surface. The stringer comprises a first flange portion and a second flange portion with the first flange portion and the second flange portion contacting the inner surface. The composite panel further comprises an integrated shim positioned on the first flange portion. The integrated shim may comprise a sacrificial material configured to be trimmed to the desired geometry. The sacrificial material may comprise a glass fiber reinforced plastic fabric pre-impregnated with resin. The integrated shim may be configured to interface with internal support structures of a wing assembly. The integrated shim may be configured to be machined to fit dimensions and measurements corresponding to the internal support structures of the wing assembly.

Stiffened composite panel with integrated shim

A composite charge is formed between two compression dies into a composite laminate stiffener. The stiffener is contoured along its length by contouring the dies. Wrinkle diffusers attached to, or embedded or incorporated into the tool surfaces of the dies, diffuse wrinkles formed on the inside radius of the stiffener during the contouring.

Wrinkle mitigation in contoured composite stiffeners

A seal arrangement is provided for sealing an exposed edge of a composite laminate part having a fay surface configured to be joined to a structure. The seal arrangement includes a precured edge seal covering the exposed edge and a cover covering the edge seal. A seal bead located within a recess in the fay surface of the part forms a seal between the part and the structure.

Part edge seal arrangement and joining method

Examples include an apparatus configured for attaching a rib of an aircraft wing to a panel of the aircraft wing, the apparatus including: an insert that is configured to be attached, via an interference fit, to a hole in the rib; a shear tie including a socket at a first end of the shear tie, where the shear tie is configured to be attached to the panel at a second end of the shear tie; a ball stud including a shaft and a ball that is opposite the shaft, where the shaft is configured to be attached to the insert and the ball is configured to be positioned within the socket; and a fastener that is configured to secure the ball within the socket, thereby attaching the ball stud to the shear tie.

Apparatus for attaching aircraft wing structural components

A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer may also include a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer may also include a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

Solid laminate stringer

Aircraft wings and aircraft including such aircraft wings are disclosed. An example apparatus includes an aircraft wing having a first panel; a second panel; ribs coupled between the first and second panels; and stiffeners coupled between the ribs in a spanwise direction and to the first panel, the coupling between the stiffeners and the first panel to deter axial loads from being received by the stiffeners, the stiffeners to increase a compressional stability of the first panel, wherein the coupling between the stiffeners and the first panel are indirect couplings formed via clips, the couplings formed via the clips deter the axial loads from being received by the stiffeners while increasing the compressional stability of the first panel.

Aircraft wings and aircraft including such aircraft wings

A solid laminate stringer includes a base segment that forms a first generally trapezoidal cross section. The solid laminate stringer also includes a transition segment abutting the base segment, with concave sides that are continuous with the sides of the base segment. The solid laminate stringer also includes a top segment abutting the transition segment, where the top segment forms a second generally trapezoidal cross section with sides that are continuous with the concave sides of the transition segment. The solid laminate stringer also includes a first overwrap layer covering the top segment, the transition segment, and at least a portion of the base segment. The solid laminate stringer also includes a second overwrap layer overlapping at least a portion of the first overwrap layer covering the base segment.

A window frame assembly for an aircraft, includes a window frame of composite material, adapted for attachment in a window opening of an aircraft, having an outer flange with an exterior surface and an interior surface, a metal erosion shield attached to the exterior surface of the outer flange, and a polymer adapter ring, attached to the interior surface of the outer flange. The window frame has a substantially constant thickness, and the erosion shield has a substantially constant cross-sectional shape. The adapter ring has a sloped engagement surface configured for supporting a window pane assembly.

Window frame assembly for aircraft

Growing community of inventors

Seattle, WA, United States of America

Ian E Schroeder